KR102071324B1 - Nozzle for combustor, combustor, and gas turbine including the same - Google Patents

Abstract

The present invention provides a nozzle, a combustor, and a gas turbine capable of efficiently atomizing fuel.
Combustor nozzle according to an aspect of the present invention, the outer tube, the first inner tube which is provided inside the outer tube to form an air passage between the outer tube, the inner inner tube is provided A second inner tube defining a main fuel passage between the first inner tube and a pilot fuel passage therein; And a splash plate defining a first space connected to the main flue passage and the air passage and an injection slot connected to the first space between the outer tube and the splash plate, wherein the splash plate extends outward toward the tip. do.

Description

NOZZLE FOR COMBUSTOR, COMBUSTOR, AND GAS TURBINE INCLUDING THE SAME}

The present invention relates to a combustor nozzle, a combustor, and a gas turbine comprising the same.

The gas turbine is a power engine that mixes and burns compressed air and fuel compressed in a compressor, and rotates the turbine with hot gas generated by combustion. Gas turbines are used to drive generators, aircraft, ships and trains.

Gas turbines generally include compressors, combustors, and turbines. The compressor sucks and compresses the outside air and delivers it to the combustor. The compressed air in the compressor is at high pressure and high temperature. The combustor mixes and combusts compressed air and fuel introduced from the compressor. The combustion gases generated by the combustion are discharged to the turbine. The combustion gas causes the turbine blades inside the turbine to rotate, thereby generating power. The generated power is used in various fields such as power generation and driving of mechanical devices.

Fuel is injected through nozzles installed in each combustor and the nozzles can inject liquid fuel. These nozzles typically include liquid atomization nozzles that spray a quantity of fuel into the combustion chamber. The nozzle needs to be simple in structure and capable of atomizing fuel efficiently.

Republic of Korea Patent No. 10-1760736

Based on the technical background as described above, the present invention seeks to provide a nozzle, a combustor, and a gas turbine capable of atomizing fuel efficiently.

Combustor nozzle according to an aspect of the present invention, the outer tube, the first inner tube which is provided inside the outer tube to form an air passage between the outer tube, the inner inner tube is provided A second inner tube defining a main fuel passage between the first inner tube and a pilot fuel passage therein; And a splash plate defining a first space connected to the main flue passage and the air passage and an injection slot connected to the first space between the outer tube and the splash plate, wherein the splash plate extends outward toward the tip. do.

Here, the injection slot may be formed between the outer peripheral surface of the outer tube and the tip of the splash plate.

In addition, a plurality of struts spaced apart in the circumferential direction of the first space and connected to the splash plate and the outer tube may be installed in the first space.

The first space may include a divided region divided by the strut and a connection region formed in a circumferential direction of the splash plate.

In addition, a first barrier may be formed between the first space and the air passage, and a plurality of first connection holes connecting the first space and the air passage may be formed in the first barrier.

In addition, a second barrier may be formed between the first space and the main fuel passage, and a plurality of second connection holes may be formed in the second barrier to connect the first space and the main fuel passage.

In addition, an injection hole may be formed at a tip of the pilot fuel passage, and a curtain barrier may be formed in front of the injection hole, and a plurality of air curtain holes may be formed in the curtain barrier. have.

The air curtain hole may be connected to the air passage via a plurality of connection passages, and the cooling passages may be connected to the connection passages extending in the circumferential direction of the second inner tube.

In addition, the front end of the nozzle is formed with the inclined portion formed by the splash plate and the inclined portion is formed with a flat plate portion formed in the plane and the recessed portion formed in the flat plate portion, the curtain barrier is formed on the side of the groove portion, The injection hole may be formed at the bottom of the groove.

In addition, a flow guide member may be installed in the pilot fuel passage, and the flow guide member may include a head portion having a guide groove formed spirally on an outer circumferential surface thereof.

In addition, the flow guide member is connected to the head portion and further comprises a guide tube having a distribution flow path formed therein, the rear end of the guide tube is formed with an inlet passage connected to the distribution flow path, A plurality of outlet passages connected to the distribution passage may be formed.

In addition, the outer circumferential surface of the guide tube formed with the outlet passage may be formed so that the outer diameter gradually decreases toward the tip.

In addition, the head portion may be connected to the conical guide projection protruding to the rear of the head portion.

In addition, a plurality of channels may be formed on an outer circumferential surface of the guide protrusion extending from the center of the guide protrusion to the outside but extending in the longitudinal direction of the guide protrusion.

On the other hand, a burner having a plurality of nozzles for injecting fuel and air according to another aspect of the present invention, the duct assembly coupled to one side of the burner and the fuel and the air is burned in the interior and delivers the burned gas to the turbine The combustor which includes the said nozzle is a 1st inner side tube provided in the inside of the said outer side tube and the said outer side tube, and forms an air path between the said outer side tube, and the inside of the said 1st inner side tube, A second inner tube defining a main fuel passage between the first inner tube and a pilot fuel passage therein; a first space connected to the main fuel passage and the air passage between the outer tube and the first inner tube; It may include a splash plate to form an injection slot connected to the first space and to diffuse the fuel delivered from the main fuel passage.

On the other hand, a compressor for compressing the air introduced from the outside according to another aspect of the present invention, a combustor for mixing by mixing the compressed air and fuel compressed in the compressor and a plurality of turbines rotated by the combustion gas burned in the combustor In the gas turbine including a turbine including a blade, the combustor is coupled to one side of the burner and a burner having a plurality of nozzles for injecting fuel and air, the fuel and the air is burned in the interior and burned gas And a duct assembly for delivering to a turbine, wherein the nozzle comprises: a first inner tube installed inside the outer tube and forming an air passage between the outer tube and the first tube; Installed inside the inner tube to form a main fuel passage between the first inner tube and a pilot fuel passage therein. And a splash plate for forming a second inner tube and a first space between the outer tube and a first space connected to the main fuel passage and the air passage and an injection slot connected to the first space. An injection hole may be formed at the front end of the injection hole, and a curtain barrier may be formed in front of the injection hole, and a plurality of air curtain holes connected to an air passage may be formed in the curtain barrier.

As described above, according to the nozzle, the combustor, and the gas turbine according to one aspect of the present invention, the fuel can be efficiently atomized using the splash plate.

In addition, an air curtain hole may be formed to perform efficient cooling while atomizing the pilot fuel. In addition, a strut is formed so that the widely formed splash plate can be stably supported by the outer tube.

1 is a view showing the inside of a gas turbine according to a first embodiment of the present invention.
FIG. 2 shows the combustor of FIG. 1.
3 is a perspective view showing a nozzle according to a first embodiment of the present invention.
FIG. 4 is a view taken along the line IV-IV of FIG. 3.
FIG. 5 is a view taken along the line VV of FIG. 3.
6 is a perspective view showing a flow guide member according to a first embodiment of the present invention.
7 is a sectional view showing a nozzle according to a second embodiment of the present invention.
8 is a perspective view showing a flow guide member according to a second embodiment of the present invention.
9 is a sectional view showing a nozzle according to a third embodiment of the present invention.
10 is a perspective view showing a flow guide member according to a third embodiment of the present invention.

As the invention allows for various changes and numerous embodiments, particular embodiments will be illustrated and described in detail in the detailed description. However, this is not intended to limit the present invention to specific embodiments, it should be understood to include all transformations, equivalents, and substitutes included in the spirit and scope of the present invention.

The terminology used herein is for the purpose of describing particular example embodiments only and is not intended to be limiting of the present invention. Singular expressions include plural expressions unless the context clearly indicates otherwise. In the present invention, the terms 'comprise' or 'having' are intended to indicate that there is a feature, number, step, operation, component, part, or combination thereof described in the specification, and one or more other features. It is to be understood that the present invention does not exclude the possibility of the presence or the addition of numbers, steps, operations, components, components, or a combination thereof.

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings. At this time, it is noted that the same components in the accompanying drawings are represented by the same reference numerals as possible. In addition, detailed descriptions of well-known functions and configurations that may blur the gist of the present invention will be omitted. For the same reason, in the accompanying drawings, some components are exaggerated, omitted or schematically illustrated.

Hereinafter, a gas turbine according to a first embodiment of the present invention will be described.

1 is a view showing the inside of a gas turbine according to an embodiment of the present invention, Figure 2 is a view showing the combustor of FIG.

The thermodynamic cycle of the gas turbine 1000 according to this embodiment may ideally follow the Brayton cycle. The Brayton cycle may consist of four processes leading to isotropic compression (thermal insulation compression), static pressure quenching, isotropic expansion (thermal insulation expansion), and constant pressure heat dissipation. In other words, the air is sucked in and compressed to high pressure, and the fuel is combusted in a constant pressure environment to release thermal energy, and the high-temperature combustion gas is expanded and converted into kinetic energy to release exhaust gas containing residual energy into the atmosphere. Can be. That is, the cycle may be performed in four processes of compression, heating, expansion, and heat dissipation.

As shown in FIG. 1, the gas turbine 1000 realizing the Brayton cycle may include a compressor 1100, a combustor 1200, and a turbine 1300. Although the following description will refer to FIG. 1, the description of the present invention can also be widely applied to a turbine engine having a configuration equivalent to that of the gas turbine 1000 illustrated by way of example in FIG. 1.

Referring to FIG. 1, the compressor 1100 of the gas turbine 1000 may suck air from the outside and compress the air. The compressor 1100 may supply compressed air compressed by the compressor blade 1130 to the combustor 1200, and also supply cooling air to a high temperature region requiring cooling in the gas turbine 1000. At this time, since the sucked air is subjected to the adiabatic compression process in the compressor 1100, the pressure and temperature of the air passing through the compressor 1100 are increased.

Compressor 1100 is designed as centrifugal compressors or axial compressors. In small gas turbines, centrifugal compressors are applied, whereas large gas turbines 1000 as shown in FIG. Since it is necessary to compress the multistage axial compressor 1100 is generally applied. At this time, in the multi-stage axial compressor 1100, the blade 1130 of the compressor 1100 rotates in accordance with the rotation of the rotor disk to move the compressed air to the compressor vane 1140 of the rear stage while compressing the air introduced. Air is compressed at higher pressure as it passes through the blade 1130 formed in multiple stages.

The compressor vane 1140 may be mounted inside the housing 1150, and a plurality of compressor vanes 1140 may be mounted in a stage. The compressor vane 1140 guides the compressed air moved from the compressor blade 1130 at the front end to the blade 1130 at the rear end. In one embodiment, at least some of the plurality of compressor vanes 1140 may be rotatably mounted within a predetermined range for adjusting the inflow amount of air.

The compressor 1100 may be driven using a portion of the power output from the turbine 1300. To this end, as shown in FIG. 1, the rotating shaft of the compressor 1100 and the rotating shaft of the turbine 1300 may be directly connected to each other. In the case of the large gas turbine 1000, almost half of the output produced by the turbine 1300 may be consumed to drive the compressor 1100. Thus, improving the efficiency of the compressor 1100 has a direct impact on improving the overall efficiency of the gas turbine 1000.

On the other hand, the combustor 1200 may mix the compressed air supplied from the outlet of the compressor 1100 with the fuel and isostatically burned to produce a high energy combustion gas. 2 shows an example of a combustor 1200 applied to the gas turbine 1000. Combustor 1200 may include combustor casing 1210, burner 1220, nozzle 1400, duct assembly 1280.

The combustor casing 1210 may surround the plurality of burners 1220 and have a substantially circular shape. Burner 1220 is disposed downstream of compressor 1100 and may be disposed along an annular combustor casing 1210. Each burner 1220 is provided with several nozzles 1400, and the fuel injected from the nozzles 1400 is mixed with air at an appropriate ratio to achieve a state suitable for combustion.

In the gas turbine 1000, a gas fuel and a liquid fuel, or a combination fuel thereof may be used. It is important to create a combustion environment to reduce the amount of emissions such as carbon monoxide and nitrogen oxide, which are legally regulated. Although combustion control is relatively difficult, it has the advantage of reducing emissions by lowering combustion temperature and making uniform combustion. In recent years, a lot of premixed combustion is applied.

In the case of premixed combustion, compressed air is mixed with fuel pre-injected in the nozzle 1400 and then enters the combustion chamber 1240. The initial ignition of the premixed gas is done using an igniter, and then combustion is maintained by supplying fuel and air once the combustion is stable.

Referring to FIG. 2, the compressed air flows along the outer surface of the duct assembly 1280 through which the burner 1220 and the turbine 1300 flow, and the hot combustion gas flows, and is supplied toward the nozzle 1400. The duct assembly 1280 heated by the hot combustion gas is appropriately cooled.

Duct assembly 1280 may include a liner 1250, a transition piece 1260, and a flow sleeve 1270. The duct assembly 1280 has a double structure in which the flow sleeve 1270 surrounds the outside of the liner 1250 and the transition piece 1260, and the compressed air penetrates into the annular space inside the flow sleeve 1270 to form the liner 1250. ) And the transition piece 1260 are cooled.

The liner 1250 is a tubular member connected to the burner 1220 of the combustor 1200, and a space inside the liner 1250 forms the combustion chamber 1240. One longitudinal end of the liner 1250 is coupled to the burner 1220 and the other longitudinal end of the liner 1250 is coupled to the transition piece 1260.

And, the transition piece 1260 is connected to the inlet of the turbine 1300 serves to guide the hot combustion gas to the turbine 1300. One longitudinal end of the transition piece 1260 is coupled with the liner 1250, and the other longitudinal end of the transition piece 1260 is coupled with the turbine 1300. The flow sleeve 1270 protects the liner 1250 and the transition piece 1260 while preventing hot air from being discharged directly to the outside.

3 is a perspective view showing a nozzle according to a first embodiment of the present invention. Referring to FIG. 3, the nozzle 1400 includes an outer tube 1410, a first inner tube 1420, a second inner tube 1430, a splash plate 1440, and a flow guide member 1480. .

The outer tube 1410 consists of a substantially circular tube and has an inner space. A shroud (not shown) may be installed at an outer side of the outer tube 1410 to surround the outer tube 1410 and guide the flow of air.

The first inner tube 1420 may be inserted into the outer tube 1410 and installed coaxially with the outer tube 1410. The first inner tube 1420 defines an air passage 1411 with the outer tube 1410. The first inner tube 1420 is a tube in a circular shape and has an inner space. The second inner tube 1430 may be inserted into the first inner tube 1420 and installed coaxially with the first inner tube 1420. The second inner tube 1430 forms a main fuel passage 1421 between the first inner tube 1420. In addition, the second inner tube 1430 may be formed of a circular tube, and a pilot fuel passage 1431 may be formed inside the second inner tube 1430.

The main fuel passage 1421 may be supplied with a mixed fuel in the form of an emulsion in which water and fuel are mixed, and the liquid fuel may be supplied to the pilot fuel passage 1431. In this case, the fuel may be made of diesel, but the present invention is not limited thereto. In addition, gas fuel may be supplied to the main fuel passage 1421 and the pilot fuel passage 1431.

4 is a view taken along the line IV-IV in FIG. 3, and FIG. 5 is a view taken along the line V-V in FIG.

Referring to FIGS. 3 to 5, the splash plate 1440 has a side that is inclined to extend outwardly toward the tip, and the splash plate 1440 may be formed of a plate having a substantially truncated cone shape. The splash plate 1440 may be connected to the front end of the second inner tube 1430 or may be inserted into the front end of the second inner tube 1430.

The splash plate 1440 is spaced apart from the outer tube 1410 to form the first space 1413 and the injection slot 1416 between the outer tube 1410. The splash plate 1440 diffuses the fuel introduced into the first space 1413.

The first space 1413 may be formed between the outer circumferential surface of the splash plate 1440 and the inner circumferential surface of the outer tube 1410 and may extend in the circumferential direction of the splash plate 1440. The injection slot 1416 is formed between the outer circumferential surface of the outer tube 1410 and the tip of the splash plate 1440, and is formed to extend in the circumferential direction of the splash plate 1440, and may be divided by the strut 1415.

The first space 1413 is provided with a plurality of struts 1415 disposed spaced apart in the circumferential direction of the first space 1413, and the struts 1415 connect and support the splash plate 1440 and the outer tube 1410. do. The strut 1415 may be formed in a substantially flat plate shape and supports the splash plate 1440 to be stably fixed to the outer tube 1410.

The strut 1415 is formed to extend inwardly from the tip of the first space 1413 and is formed only in a part of the first space 1413, so that the first space 1413 is divided by the strut 1415. And a connection region S2 formed in a circumferential direction of the S1 and the splash plate 1440.

A first barrier 1451 is formed between the first space 1413 and the outer tube 1410, and a second barrier 1452 is formed between the first space 1413 and the first inner tube 1420. Here, the first barrier 1451 may be formed to be inclined so that the outside protrudes further toward the front, and the second barrier 1452 may be formed to be inclined so that the inside more protrudes to the front. The first barrier 1451 and the second barrier 1452 may extend in the circumferential direction of the nozzle 1400 to have a substantially annular shape.

A plurality of first connection holes 1457 are formed in the first barrier 1451, and the first space 1413 and the air passage 1411 may be connected to each other by the first connection holes 1575. A plurality of second connection holes 1456 are formed in the second barrier 1452, and the main fuel passage 1421 and the first space 1413 may be connected by the second connection holes 1456. Accordingly, the first space 1413 is connected to the air passage 1411 and the main fuel passage 1421 so that air and fuel can be introduced into the first space 1413. The first connection hole 1457 may be formed in a direction toward the center of the nozzle 1400, and the second connection hole 1456 may be formed in a direction toward the outside of the nozzle 1400.

The fuel delivered from the second connection hole 1456 to the first space 1413 travels along the surface of the splash plate 1440 while hitting the splash plate 1440 as a mixed fuel in the form of an emulsion of water and fuel. At this time, since the air introduced from the first connection hole 1575 is injected toward the surface of the splash plate 1440, the mixed fuel is spread thinly and widely on the surface of the splash plate 1440. The mixed fuel moved to the injection slot along the splash plate 1440 may be atomized and sprayed while leaving the tip of the splash plate 1440. In addition, air is discharged with the mixed fuel to the injection slot 1416 while cooling the splash plate 1440 and the outer tube 1410.

On the other hand, an injection hole 1432 having a smaller inner diameter than the periphery may be formed at the tip of the first nozzle 1400, and fuel may be injected into the pilot fuel passage 1431 through the injection hole 1432. The second inner tube 1430 may be formed to gradually decrease the inner diameter toward the injection hole 1432.

A curtain barrier 1453 may be formed at the front of the injection hole 1432 to surround the front space of the injection hole 1432, and a plurality of air curtain holes 1458 connected to the air passage may be formed at the curtain barrier 1453. . The curtain barrier 1453 may have a circular ring shape.

The tip of the nozzle 1400 is connected to the bottom of the inclined portion (1441) and the inclined portion (1441) formed by the splash plate 1440, the groove portion formed in the flat plate portion 1442 and the flat plate portion (1442) The 1443 is formed, the side surface of the groove 1443 forms a curtain barrier 1453, and the injection hole 1432 is formed in the bottom of the groove 1443.

Meanwhile, the second connection hole 1456 is formed in the thickness direction of the second barrier 1452, and the second barrier 1452 is formed with a plurality of connection passages 1451 extending in the width direction of the second barrier 1452. do. The connecting passage runs in a direction crossing the second connecting hole but is not in communication with the second connecting hole.

The plurality of connection passages 1461 connect the air passages 1411 and the air curtain holes 1458 to transfer air from the air passages 1411 to the air curtain holes 1458. The cooling passages 1462 may be connected to the connection passages 1411 in the circumferential direction of the second inner tube 1430, and the cooling guide passages 1462 may be connected to the air curtain holes 1458. Therefore, the air introduced from each connection passage 1541 merges in the cooling guide flow path 1462 and then moves to the air curtain hole 1458.

Air enters the cooling guide flow path 1462 through the connection passage 1541 to cool the tip of the second inner tube 1430, and is discharged through the air curtain hole 1458 to cool the air curtain hole 1458. . In addition, the air is discharged through the air curtain hole 1458 to help atomize the fuel as well as to maintain a pressure difference between the inside and the outside of the main fuel passage 1421 and prevent the flame or the combustion gas from flowing back.

6 is a perspective view showing a flow guide member according to a first embodiment of the present invention.

Referring to FIGS. 5 and 6, the flow guide member 1480 is inserted into the pilot fuel passage 1431, and the flow guide member 1480 includes the head portion 1148 and the head portion 1148. It is connected to include a guide pipe (1482) formed in the distribution passage 1484 therein. The head portion 1148 has a substantially cylindrical shape and has a guide groove 1483 helically formed on an outer circumferential surface thereof. A plurality of guide grooves 1483 are formed in the head portion 1148, and the guide grooves 1483 are formed extending from the rear end to the tip of the head portion 1148.

The outer surface of the head portion 1148 is installed to abut the outer surface of the second inner tube 1430, so that the fuel can move only through the guide groove (1483). Guide grooves 1483 extend spirally to form swirls in the flow of fuel. The front surface of the head portion 1148 may be a flat surface, and the rear surface of the head portion 1441 may be an inclined surface.

A dispersion passage 1484 extending in the longitudinal direction of the guide tube 1462 is formed in the guide tube 1462, and an inlet passage 1485 connected to the dispersion passage 1484 is formed at a rear end of the guide tube 1462. On the outer circumference of the guide tube 1462, a plurality of outlet passages 1486 connected to the distribution passage 1484 are connected to each other. The inlet passage may be formed such that the inner diameter gradually decreases from the rear to the front.

Three outlet passages 1486 may be formed in the guide tube 1462, and the outlet passage 1486 may be formed to be inclined outwardly from the center of the guide tube 1462. When the outer circumferential surface of the guide tube 1462 having the outlet passage 1486 is formed to be inclined, the outer diameter may be gradually reduced toward the front. The guide pipe 1462 divides the flow of the fuel into three, and the divided fuel moves along the guide groove 1483 formed in the head portion 1148 to form a swirl, and then is discharged through the injection hole 1432. .

As described above, according to the first embodiment, the splash plate 1440 forms the first space 1413 and the injection slot 1416, and the first space 1413 is connected to the first connection hole 1457 and the second connection. Since the hole 1456 is connected to the air passage 1411 and the main fuel passage 1421, the mixed fuel moving through the main fuel passage 1421 can be atomized more easily, and the splash plate 1440 can be efficiently Can be cooled. In addition, a splash plate 1440 having a relatively large area may be stably fixed to the outer tube 1410 by the strut 1415. In addition, an air curtain hole 1458 is formed in the curtain barrier 1453 to efficiently inject the pilot fuel while cooling the tip of the nozzle 1400 efficiently.

Hereinafter, a nozzle according to a second embodiment of the present invention will be described. 7 is a cross-sectional view showing a nozzle according to a second embodiment of the present invention, Figure 8 is a perspective view showing a flow guide member according to a second embodiment of the present invention.

Referring to FIGS. 7 and 8, the nozzle 2400 according to the second exemplary embodiment has the same structure as the nozzle according to the first exemplary embodiment except for the flow guide member 2450. Duplicate description of the description will be omitted.

The flow guide member 2450 is inserted into the pilot fuel passage 1431, and the flow guide member 2450 includes a head part 2251 and a guide protrusion 2452 connected to the head part 2251. The head portion 2251 is formed in a substantially cylindrical shape, and a guide groove 2453 helically connected to the outer circumferential surface is formed. A plurality of guide grooves 2453 are formed in the head portion 2251, and the guide grooves 2453 are formed extending from the rear end to the tip of the head portion 2251. Guide grooves 2453 are spiraled to form swirls in the flow of fuel. The front and rear surfaces of the head part 2251 may be formed in a plane. The guide protrusion 2452 is formed to protrude rearward from the rear of the head portion 2251 and may have a cylinder having an outer diameter smaller than that of the head portion 2251.

Hereinafter, a nozzle according to a third embodiment of the present invention will be described. 9 is a cross-sectional view showing a nozzle according to a third embodiment of the present invention, Figure 10 is a perspective view showing a flow guide member according to a third embodiment of the present invention.

9 and 10, the nozzle 3400 according to the third exemplary embodiment has the same structure as the nozzle according to the first exemplary embodiment except for the flow guide member 3450. Duplicate description of the description will be omitted.

The flow guide member 3450 is inserted into the pilot fuel passage 1431, and the flow guide member 3450 includes a head portion 3501 and a guide protrusion 3452 connected to the head portion 3651. The head portion 3651 has a substantially cylindrical shape, and guide grooves 3345 are formed on the outer circumferential surface in a straight line. A plurality of guide grooves 3345 are formed in the head portion 3651, and the guide grooves 3345 are formed extending from the rear end to the tip of the head portion 3651. Guide grooves 3345 continue spirally to form swirls in the flow of fuel. The front and rear surfaces of the head portion 3651 may be formed in a plane. The guide protrusion 3452 is formed to protrude rearward from the rear of the head portion 3651 and may have a substantially conical shape. On the outer circumferential surface of the guide protrusion 3452, a plurality of channels 3454 extending from the center of the guide protrusion 3452 and extending in the longitudinal direction of the guide protrusion 3452 may be formed, and the channel 3454 may include a guide groove. Can be connected. Thereby, fuel which moves along the pilot fuel passage 1431 can be guided more easily.

As mentioned above, although an embodiment of the present invention has been described, those of ordinary skill in the art may add, change, delete or add elements within the scope not departing from the spirit of the present invention described in the claims. The present invention may be modified and changed in various ways, etc., which will also be included within the scope of the present invention.

1000: gas turbine
1100: compressor
1130: compressor blade
1140: vane
1150: housing
1200: burner
1210: combustor casing
1220: burner
1240: combustion chamber
1400: nozzle
1410: outer tube
1411: air passage
1420: first inner tube
1421: main fuel passage
1430: second inner tube
1432: spray hole
1453: curtain barrier
1458 air curtain hall
1431: Pilot Fuel Pathway
1440: splash plate
1413: first space
1415: strut
1416: spray slot
1451: first barrier
1452: Second Barrier
1457: first connecting hole
1456: second connection hole
1461: connecting passage
1462: cooling guide flow path
1480, 2450, 3450: flow guide member
1481, 2451, 3451: head portion
1482: guide tube
1483, 2453: guide groove
1484 Decentralized Euro
1485: entrance passage
1486: exit passage
2452, 3452: Guide turning
3454: channel

Claims (16)

In the nozzle for the combustor,
Outer tube;
A first inner tube installed inside the outer tube to form an air passage therebetween;
A second inner tube installed inside the first inner tube to form a main fuel passage between the first inner tube and a pilot fuel passage therein; And
And a splash plate formed between the outer tube and the main flue passage and the air passage to form a first space and an injection slot connected to the first space.
The splash plate is extended outward toward the tip,
And the first space includes a divided section (S1) connected to the injection slot and a connection area (S2) connected to the fuel passage and the air passage. According to claim 1,
And the injection slot is formed between the outer circumferential surface of the outer tube and the tip of the splash plate. In the nozzle for the combustor,
Outer tube;
A first inner tube installed inside the outer tube to form an air passage therebetween;
A second inner tube installed inside the first inner tube to form a main fuel passage between the first inner tube and a pilot fuel passage therein; And
And a splash plate formed between the outer tube and the main flue passage and the air passage to form a first space and an injection slot connected to the first space.
The splash plate is extended outward toward the tip,
The first space is spaced apart in the circumferential direction of the first space, the nozzle for the combustor, characterized in that a plurality of struts connecting the splash plate and the outer tube is installed. The method of claim 3, wherein
And the first space includes a divided region divided by the strut and a connecting region formed in a circumferential direction of the splash plate. In the nozzle for the combustor,
Outer tube;
A first inner tube installed inside the outer tube to form an air passage therebetween;
A second inner tube installed inside the first inner tube to form a main fuel passage between the first inner tube and a pilot fuel passage therein; And
And a splash plate formed between the outer tube and the main flue passage and the air passage to form a first space and an injection slot connected to the first space.
The splash plate is extended outward toward the tip,
And a first barrier is formed between the first space and the air passage, and the first barrier has a plurality of first connection holes connecting the first space and the air passage. The method of claim 5,
A second barrier is formed between the first space and the main fuel passage, and the second barrier has a plurality of second connection holes connecting the first space and the main fuel passage. . According to claim 1,
An injection hole is formed at the front end of the pilot fuel passage, and a curtain barrier is formed in front of the injection hole, and a plurality of air curtain holes connected to the air passage are formed in the curtain barrier. Combustor nozzles. The method of claim 7, wherein
The air curtain hole is connected to the air passage via a plurality of connecting passages, the connecting passage is a nozzle for a combustor, characterized in that the cooling guide flow path extending in the circumferential direction of the second inner tube is connected. The method of claim 7, wherein
The inclined portion formed by the splash plate and the inclined portion formed by the splash plate and a flat plate portion made of a flat portion and a recessed portion formed in the flat plate portion is formed at the tip of the nozzle, the curtain barrier is formed on the side of the groove portion, Combustor nozzle, characterized in that the injection hole is formed in the bottom of the portion. According to claim 1,
A flow guide member is installed inside the pilot fuel passage, and the flow guide member comprises a head portion having a guide groove formed in a spiral shape on an outer circumferential surface thereof. The method of claim 10,
The flow guide member further includes a guide tube connected to the head part and having a distribution channel formed therein, and an inlet passage connected to the distribution channel is formed at a rear end of the guide tube, and the dispersion is formed at an outer circumference of the guide tube. A combustor nozzle, characterized in that a plurality of outlet passages connected to the flow path is formed. The method of claim 11, wherein
Combustor nozzles, characterized in that the outer peripheral surface of the guide tube formed with the outlet passage is formed so that the outer diameter gradually decreases toward the tip. The method of claim 10,
Combustor nozzle, characterized in that the head portion is formed with a conical guide projection protruding rearward of the head portion. The method of claim 13,
Combustor nozzles, characterized in that formed on the outer circumferential surface of the guide projections extending from the center of the guide projection to the outside but extending in the longitudinal direction of the guide projection. A burner having a plurality of nozzles for injecting fuel and air, the combustor comprising a duct assembly coupled to one side of the burner and the fuel and the air is internally burned and delivers the burned gas to a turbine,
The nozzle may include an outer tube, a first inner tube provided inside the outer tube to form an air passage between the outer tube, and a first inner tube provided inside the first inner tube. A second inner tube defining a main fuel passage between the second inner tube and a pilot fuel passage therein, and a first space connected to the main fuel passage and the air passage between the outer tube and the first space; A splash plate forming an injection slot, said splash plate diffusing fuel delivered from said main fuel passage,
And the first space includes a divided region (S1) connected to the injection slot and a connection region (S2) connected to the fuel passage and the air passage. A gas turbine including a compressor including a compressor for compressing air introduced from the outside, a combustor which mixes and combustes compressed air and fuel compressed by the compressor, and a plurality of turbine blades that are rotated by the combustion gas combusted by the combustor. As
The combustor includes a burner having a plurality of nozzles for injecting fuel and air, and a duct assembly coupled to one side of the burner, the fuel and air being combusted therein, and delivering a combusted gas to a turbine,
The nozzle may include an outer tube, a first inner tube provided inside the outer tube to form an air passage between the outer tube, and a first inner tube provided inside the first inner tube. A second inner tube defining a main fuel passage between the second inner tube and a pilot fuel passage therein, and a first space connected to the main fuel passage and the air passage between the outer tube and the first space; A splash plate forming an injection slot,
Injection holes are formed at the front end of the pilot fuel passage, a curtain barrier is formed in front of the injection hole to surround the front space of the injection hole, the curtain barrier is formed with a plurality of air curtain holes connected to the air passage,
The air curtain hole is connected to the air passage through a plurality of connecting passages,
A second barrier is formed between the first space and the main fuel passage;
And a plurality of second connection holes and the connection passages connecting the first space and the main fuel passage to the second barrier.

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